ТЕХНОЛОГІЧНІ ОСОБЛИВОСТІ ВИГОТОВЛЕННЯ ВНУТРІШНЬОГО ТЕПЛОЗАХИСТНОГО ПОКРИТТЯ ДЛЯ РАКЕТНИХ ТВЕРДОПАЛИВНИХ ДВИГУНІВ

The article presents the main results of works related to material creation and study, and development of manufacturing technology of inner heat-protection cover made of composite materials in Yuzhnoye SDO for solid propellant rocket engines. Typically, this coating is a multi-layer structure, which consists of: sealing layer; main thermal protection coating; barrier layer;   securing layer. Thermal protective coating (TPS) of the ends and cuffs are made of rubber bands on the application form followed by molding in an autoclave. On the shape for bottoms TPC manufacturing shall be placed dividing (protecting) layers, protective binding layer materials and layer by layer shall be putted the cutted rubber blanks to obtain the required thickness. Lock parts of cuffs, compensators, releasing TPC and body flange shall be installed in required areas. TPC curing is performed incompletely for providing the required properties of TPC material during the thermal treatment jointly with body. Cylindrical part TPC is put on the mandrel layer wise: the barrier layer, the separation layer, main heat shield and a sealing layer. Glue is applied between the main TPC, the sealing layer and the load-bearing shell. The article presents the technological characteristics of inner heat-protection cover manufacturing for solid propellant rocket engines and technical configuration of the production base.